CN112483190B

CN112483190B - Turbine blade based on aeroengine possesses vortex structure

Info

Publication number: CN112483190B
Application number: CN202011362447.5A
Authority: CN
Inventors: 邹宗果; 毕克文; 卢玉章; 董加胜; 申健; 王威; 李祝雁; 朱辉; 潘月栋; 沙伟; 李莲鹏; 赵纪彬; 岳金玲
Original assignee: Rizhao Liyang Industrial Equipment Co ltd
Current assignee: Rizhao Liyang Industrial Equipment Co ltd
Priority date: 2020-11-27
Filing date: 2020-11-27
Publication date: 2022-05-13
Anticipated expiration: 2040-11-27
Also published as: CN112483190A

Abstract

The invention provides a turbine blade with a turbulent flow structure based on an aeroengine, which comprises a turbine assembly and a supporting and reinforcing structure, wherein the turbine assembly is provided with a turbine blade body; the turbine assembly is formed by connecting an upper turbine, a middle turbine, a lower turbine and a middle penetrating column; the middle turbine card is gone into in the draw-in groove of lower turbine top side, the middle fixed intermediate of turbine under of wearing to prop up, and the middle post of wearing still upwards wears out middle turbine through middle perforation, still be equipped with spacing slot on the top face of middle turbine, and go up the spacing post of inserting of turbine bottom side and insert in spacing slot, still be connected with twelve groups of outer connecting cylinders on the outer wall of lower turbine, support reinforced structure and connect respectively on outer connecting cylinder and support on blade A and blade B. When turbine assembly rotational speed was higher, the air current flowed to the air flue and flowed out through the vortex pipe along the air current hole flow direction air flue in the middle of the air baffle A, increased the air current around the turbine assembly, through setting up support reinforced structure, improved the holistic intensity of blade.

Description

Turbine blade based on aeroengine possesses vortex structure

Technical Field

The invention belongs to the technical field of aeroengine turbines, and particularly relates to a turbine blade with a turbulent flow structure based on an aeroengine.

Background

The turbine is one of important parts in an aviation gas turbine engine, the turbine plays a role in converting most of available heat energy of gas into mechanical work of the turbine, the turbine blade serving as one of key parts of the engine rotates at high speed under the conditions of high temperature and high pressure, and airflow on the surface of the turbine blade is very complex, so the quality of the design of the turbine blade is related to the performance of the whole engine.

If the application number is: in CN 201920201415.3's patent, an aeroengine turbine blade is disclosed, belongs to aeroengine refrigeration technical field, solves the problem that current aeroengine turbine blade refrigerates inadequately. An aircraft engine turbine blade comprising: the cold flow device comprises a front end, a pressure surface, a suction surface and a tail end, wherein the front end, the pressure surface, the suction surface and the tail end are enclosed to form a hollow structure, and the hollow structure provides a flow channel for cold flow; at least one of the front end, the pressure surface and the suction surface is of a thin-wall structure with a heat exchange cavity in the middle, and the heat exchange cavity is respectively communicated with the hollow structure; the heat exchange cavity is communicated with the exterior of the turbine blade of the aero-engine through the air outlet reducing hole; the area of an inlet, connected with the heat exchange cavity, of the air outlet variable-diameter hole is smaller than the area of an outlet, connected with the outer portion of the turbine blade of the aero-engine, of the air outlet variable-diameter hole. According to the invention, the air outlet is set to be the variable-diameter hole with the small inside and the large outside, so that the temperature can be lowered inside and raised outside through the change of the volume of the gas, and the cooling effect is improved.

Based on the above, among the traditional engine turbine structure, its blade fin end steadiness ability is relatively poor, lacks bearing structure between the blade, and it is when operating moreover, and the turbine overall rear end does not have the vortex structure, has reduced the holistic rotational speed of turbine, dismantles and maintains also inconvenient.

Disclosure of Invention

In order to solve the technical problems, the invention provides a turbine blade with a turbulence structure based on an aeroengine, which aims to solve the problems that the stability of a tail wing end of the blade is poor, a support structure is lacked among the blades, and when the turbine blade runs, the overall rear end of the turbine has no turbulence structure, so that the rotating speed of the whole turbine is reduced, and the turbine blade is inconvenient to disassemble and maintain.

The invention is based on the purpose and the effect of a turbine blade with a turbulent flow structure of an aeroengine, and is achieved by the following specific technical means:

a turbine blade with a turbulent flow structure based on an aeroengine comprises a turbine assembly and a supporting and reinforcing structure; the turbine assembly is formed by connecting an upper turbine, a middle turbine, a lower turbine and a middle penetrating column; the middle turbine is clamped into a clamping groove on the top side of the lower turbine, the blades B are clamped into blade bayonets, the threaded connecting holes A are vertically opposite to the threaded connecting holes B respectively, the middle penetrating column is fixedly inserted in the middle of the lower turbine and penetrates out of the middle turbine upwards through the middle through hole, a limiting slot is further formed in the top end face of the middle turbine, the limiting inserting column on the bottom side of the upper turbine is inserted into the limiting slot, the blades A are arranged between the blades B, the inner ends of the blades B are attached to outer supporting blocks, the stepped bolt penetrating holes are vertically opposite to the threaded connecting holes A, the upper turbine, the middle turbine and the lower turbine penetrate into the stepped bolt penetrating holes through hexagon socket head bolts and are sequentially screwed into the threaded connecting holes A and are connected with the threaded connecting holes B respectively, and twelve groups of outer connecting cylinders are further connected to the outer wall of the lower turbine, the inside outer end of outer connecting cylinder is equipped with the step jack, and the inside inboard of outer connecting cylinder is equipped with connecting thread, support reinforced structure and connect respectively on outer connecting cylinder and support on blade A and blade B.

Furthermore, the middle of the inner side of the upper turbine is also provided with an upper through hole, the top end of the upper through hole is provided with an airflow baffle plate A, the middle of the airflow baffle plate A is provided with an airflow hole, and the outer end of the airflow hole is of an arc-shaped structure.

Furthermore, the top end of the middle penetrating column is also inserted into the upper through hole, an air passage is formed in the middle of the top of the middle penetrating column, and the air passage is formed from the top end of the middle penetrating column to the position of the internal thread cylinder and communicated with the internal thread cylinder.

Furthermore, the internal thread cylinder is provided with twelve groups, every three adjacent groups are connected together, the turbulence pipe penetrates through the outer end of the lower turbine and is screwed into the internal thread cylinder through threads, and the outer port of the turbulence pipe is of an arc-shaped structure and faces the rotating direction of the turbine assembly.

Furthermore, an airflow baffle B is movably mounted on the top end side of the air passage and attached to an airflow hole in the inner side of the airflow baffle A, and the outer diameter of the airflow baffle B is larger than the inner diameter of the airflow hole and smaller than the inner diameter of the upper through hole.

Furthermore, the bottom of the airflow baffle B is fixedly connected with a guide post, a reset spring is sleeved on the guide post, the guide post is fixedly connected with a guide block, the guide block is movably inserted into the air passage, and three groups of fan-shaped notches are formed in the outer end of the guide block.

Furthermore, the supporting and reinforcing structure comprises a T-shaped pipe, a supporting plate and a buffering column, wherein the two ends of the T-shaped pipe are respectively connected with the supporting plate through the buffering column, the supporting plate is respectively supported on the blade A and the blade B, the buffering column is slidably clamped in the pipe sleeves at the two ends of the T-shaped pipe, and a buffering spring is further arranged in the pipe sleeves at the two ends of the T-shaped pipe.

Furthermore, the other end of the T-shaped pipe is inserted into a step jack at the outer end of the inner part of the outer connecting cylinder, and a connecting bolt penetrates through the T-shaped pipe and is screwed into a connecting thread at the inner side of the inner part of the outer connecting cylinder.

The invention at least comprises the following beneficial effects:

1. the turbine assembly is formed by connecting the upper turbine, the middle turbine and the lower turbine, and is convenient to disassemble and maintain.

2. According to the invention, the airflow baffle B is arranged at the top end of the middle through column, when the rotation speed of the turbine assembly is higher, airflow pushes the airflow baffle B to extrude the return spring inwards, so that the guide block slides inwards in the air passage, and airflow flows to the air passage along the airflow hole in the middle of the airflow baffle A and flows out through the flow disturbing pipe, thereby increasing airflow around the turbine assembly and improving the rotation speed of the turbine assembly.

3. According to the invention, through arranging the supporting and reinforcing structure, the T-shaped pipe is inserted into the outer connecting cylinder and is connected and locked through the connecting bolt, so that the two groups of supporting plates are respectively attached to the rear end sides of the blade A and the blade B to support the blade A and the blade B, the integral strength of the blade is improved, meanwhile, the supporting plates can be tightly attached to the blade A and the blade B under the action of the buffer columns and the buffer and can be adjusted in a small range under the action of the buffer springs, and the blade A and the blade B are prevented from being bent rigidly.

Drawings

Fig. 1 is a schematic structural view of the present invention.

Fig. 2 is an enlarged schematic view of the structure at a in fig. 1 according to the present invention.

Fig. 3 is a schematic side view of the invention shown in fig. 1.

Fig. 4 is a schematic view of the invention shown in fig. 1 with a set of connecting bolts removed.

Fig. 5 is an enlarged view of the structure of fig. 4 at B according to the present invention.

FIG. 6 is a schematic view of the support and reinforcement structure of FIG. 4 with the upper turbine wheel removed upwardly in accordance with the present invention.

Fig. 7 is a schematic structural view of a support and reinforcement structure according to the present invention.

Fig. 8 is a schematic view of the upper turbine in the present invention.

FIG. 9 is a schematic view of the invention shown in FIG. 6 with the intermediate turbine removed upwardly and the guide blocks withdrawn from the airway.

Fig. 10 is a schematic view of the structure of the intermediate turbine in the present invention.

FIG. 11 is a schematic structural view of the lower turbine fixedly connected with the middle through column in the invention.

Fig. 12 is a schematic view of the structure of fig. 11 from another view angle according to the present invention.

Fig. 13 is a schematic view of the overall structure of the air baffle B of the present invention, and the guide post, guide block, and return spring.

In the drawings, the corresponding relationship between the component names and the reference numbers is as follows:

1. a turbine assembly; 101. an upper turbine; 1011. a blade A; 1012. perforating; 1013. an airflow baffle A; 1014. step-shaped bolt through holes; 1015. limiting and inserting the column; 1016. an outer support block; 1017. a hexagon socket head cap screw; 102. an intermediate turbine; 1021. a blade B; 1022. punching the middle of the tube; 1023. a threaded connection hole A; 1024. limiting slots; 103. a lower turbine; 1031. a card slot; 1032. a blade bayonet; 1033. an outer connecting cylinder; 1034. a threaded connection hole B; 104. penetrating a column in the middle; 1041. an air passage; 1042. an internal thread cylinder; 1043. a turbulent flow tube; 2. an airflow baffle B; 201. a guide post; 202. a guide block; 203. a return spring; 3. supporting the reinforcing structure; 301. a T-shaped pipe; 302. a support plate; 303. a buffer column; 304. and connecting the bolts.

Detailed Description

The embodiments of the present invention will be described in further detail with reference to the drawings and examples. The following examples are intended to illustrate the invention but are not intended to limit the scope of the invention.

In the description of the present invention, "a plurality" means two or more unless otherwise specified; the terms "coaxial," "bottom," "one end," "top," "middle," "other end," "upper," "side," "top," "inner," "front," "center," "two ends," and the like are used in an orientation or positional relationship indicated in the drawings for convenience in describing and simplifying the description, and are not intended to indicate or imply that the device or element being referred to must have a particular orientation, be constructed and operated in a particular orientation, and thus should not be construed as limiting the invention. Furthermore, the terms "first," "second," "third," and the like are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.

In the description of the present invention, it should be noted that, unless explicitly stated or limited otherwise, the terms "mounted," "disposed," "connected," "fixed," "screwed" and the like are to be understood broadly, and for example, they may be fixedly connected, detachably connected, or integrated; can be mechanically or electrically connected; the terms may be directly connected or indirectly connected through an intermediate, and may be communication between two elements or interaction relationship between two elements, unless otherwise specifically limited, and the specific meaning of the terms in the present invention will be understood by those skilled in the art according to specific situations.

The embodiment is as follows:

as shown in figures 1 to 13:

the invention provides a turbine blade with a turbulent flow structure based on an aeroengine, which comprises a turbine assembly 1 and a supporting and reinforcing structure 3; the turbine assembly 1 is formed by connecting an upper turbine 101, a middle turbine 102, a lower turbine 103 and a middle penetrating column 104; the middle turbine 102 is clamped into a clamping groove 1031 on the top side of the lower turbine 103, the blades B1021 are clamped into blade bayonets 1032, the threaded connecting holes A1023 are respectively vertically opposite to the threaded connecting holes B1034, the middle penetrating column 104 is fixedly inserted in the middle of the lower turbine 103, the middle penetrating column 104 further penetrates through the middle turbine 102 upwards through a middle through hole 1022, a limiting slot 1024 is further arranged on the top end face of the middle turbine 102, a limiting inserting column 1015 on the bottom side of the upper turbine 101 is inserted into the limiting slot 1024, the blades A1011 are arranged between the blades B1021, the inner ends of the blades B1021 are further attached to an outer support block 1016, the stepped bolt through holes 1014 are vertically opposite to the threaded connecting holes A1023, the upper turbine 101, the middle turbine 102 and the lower turbine 103 are inserted into the stepped bolt through an inner hexagonal bolt 1017 and are sequentially screwed into the threaded connecting holes A1023 and are respectively connected with the threaded connecting holes B1034, and twelve groups of outer connecting cylinders 1033 are further connected to the outer wall of the lower turbine 103, the inside outer end of outer connecting tube 1033 is equipped with the step jack, and the inside inboard of outer connecting tube 1033 is equipped with connecting thread, supports reinforced structure 3 and connects respectively on outer connecting tube 1033 and supports on blade A1011 and blade B1021.

Wherein, the middle of the inner side of the upper turbine 101 is further provided with an upper perforation 1012, the top end of the upper perforation 1012 is provided with an airflow baffle A1013, the middle of the airflow baffle A1013 is provided with an airflow hole, the outer end of the airflow hole is of an arc-shaped structure, the top end of the middle penetrating column 104 is further inserted into the upper perforation 1012, the middle of the top of the middle penetrating column 104 is provided with an air passage 1041, the air passage 1041 is arranged from the top end of the middle penetrating column 104 to the position of the internal thread cylinder 1042 and communicated with the internal thread cylinder 1042, the internal thread cylinder 1042 is provided with twelve groups, every three adjacent groups are connected together, the spoiler tube 1043 passes through from the outer end of the lower turbine 103 and is screwed into the internal thread cylinder 1042 through a thread, the outer port of the spoiler tube 1043 is of an arc-shaped structure and faces the rotation direction of the turbine assembly 1, the top end side of the air passage 1041 is further movably provided with an airflow baffle B2, the airflow baffle B2 is attached to the airflow hole at the inner side of the airflow baffle A1013, the outer diameter of the airflow baffle B2 is larger than the inner diameter of the airflow hole and smaller than the inner diameter of the upper perforation 1012, the bottom of the airflow baffle B2 is also fixedly connected with a guide post 201, and the guide post 201 is sleeved with a return spring 203 and is fixedly connected with a guide block 202, the guide block 202 is movably inserted in the air passage 1041, the outer end of the guide block 202 is provided with three sets of fan-shaped notches, when the rotating speed of the turbine assembly 1 is high, the airflow pushes the airflow baffle B201 to extrude the return spring 203 inwards, the guide block 202 is driven by the guide post 201 to slide inwards in the air passage 1041, so that the airflow flows to the air passage 1041 along the airflow hole in the middle of the airflow baffle a1013 and flows to the turbulent flow pipe 1043 through the three sets of fan-shaped notches on the outer side of the guide block 202, and flows out along the tail end of the turbulent flow pipe 1043, thereby increasing the airflow around the turbine assembly 1 and improving the rotating speed of the turbine assembly 1.

The supporting and reinforcing structure 3 comprises a T-shaped pipe 301, supporting plates 302 and buffering columns 303, the two ends of the T-shaped pipe 301 are respectively connected with the supporting plates 302 through the buffering columns 303, the supporting plates 302 are respectively supported on a blade a1011 and a blade B1021, the buffering columns 303 are slidably clamped in the pipe sleeves at the two ends of the T-shaped pipe 301, buffering springs are further installed in the pipe sleeves at the two ends of the T-shaped pipe 301, the other end of the T-shaped pipe 301 is inserted into a step jack at the outer end inside an outer connecting cylinder 1033, a connecting bolt 304 penetrates through the T-shaped pipe 301 and is screwed into a connecting thread on the inner side inside the outer connecting cylinder 1033, the T-shaped pipe 301 is inserted into the outer connecting cylinder 1033 and is connected with a locking position through the connecting bolt 304, so that the two groups of the supporting plates 302 are respectively attached to the rear end sides of the blade a1011 and the blade B1021, the blade a1011 and the blade B1021 are supported, the overall strength of the blade is improved, and the supporting plates 302 can be tightly attached to the blade a1011 and a blade B1021 under the effect of the buffering columns 303 and the buffering springs And the degree is adjusted, so that the hard bending between the blade A1011 and the blade B1021 is avoided.

The specific use mode and function of the embodiment are as follows:

according to the invention, the middle turbine 102 is clamped into a clamping groove 1031 on the top side of the lower turbine 103, the blades B1021 are clamped into the blade bayonet 1032, the threaded connecting holes A1023 are respectively opposite to the threaded connecting holes B1034 up and down, then the limiting insertion columns 1015 on the bottom side of the upper turbine 101 are inserted into the limiting insertion grooves 1024, the blades A1011 are arranged between the blades B1021, the inner ends of the blades B1021 are attached to the outer support blocks 1016, the stepped bolt through holes 1014 are opposite to the threaded connecting holes A1023 up and down, the two groups of supporting plates 302 are respectively attached to the rear end sides of the blades A1011 and the blades B1021 by inserting the T-shaped pipes 301 into the outer connecting cylinders 1033 and connecting and locking the blades A1023 through the connecting bolts 304, the blades A1011 and the blades B1021 are supported, the overall strength of the blades is improved, and the supporting plates 302 can be attached to the blades A1021 and the blades B1021 and can be attached to the blades B1021 under the action of the buffer columns 303 and the buffer bolts 304 and can be attached to the blades B1021 Enough adjust at a small margin under buffer spring's effect, avoid hard buckling between blade A1011 and the blade B1021, when turbine assembly 1 rotational speed is higher, the air current promotes air current baffle B201 and inwards extrudees reset spring 203, drive guide block 202 through guide post 201 and inwards slide in air flue 1041, make the air current flow to air flue 1041 along the air current hole in the middle of air current baffle A1013 and flow to vortex tube 1043 department through three sets of fan-shaped breach flow direction in the guide block 202 outside, and flow out along the end of vortex tube 1043, and then increase the air current around turbine assembly 1, improve turbine assembly 1's rotational speed.

The invention is not described in detail, but is well known to those skilled in the art.

The embodiments of the present invention have been presented for purposes of illustration and description, and are not intended to be exhaustive or limited to the invention in the form disclosed. Many modifications and variations will be apparent to those of ordinary skill in the art. The embodiment was chosen and described in order to best explain the principles of the invention and the practical application, and to enable others of ordinary skill in the art to understand the invention for various embodiments with various modifications as are suited to the particular use contemplated.

Claims

1. The utility model provides a turbine blade based on aeroengine possesses vortex structure which characterized in that: comprises a turbine assembly (1), a supporting and reinforcing structure (3); the turbine assembly (1) is formed by connecting an upper turbine (101), a middle turbine (102), a lower turbine (103) and a middle through column (104); middle turbine (102) is blocked in draw-in groove (1031) on lower turbine (103) top side, and in blade bayonet (1032) was blocked in to blade B (1021), threaded connection hole A (1023) was relative up and down with threaded connection hole B (1034) respectively, middle through-post (104) is fixed to be alternate in the centre of lower turbine (103), and middle through-post (104) still upwards worn out middle turbine (102) through middle perforation (1022), still be equipped with spacing slot (1024) on the top terminal surface of middle turbine (102), and spacing post (1015) of inserting of last turbine (101) bottom side insert spacing slot (1024) in, blade A (1011) are arranged in between blade B (1021), and the inner of blade B (1021) still pastes on outer brace (1016), and step bolt perforation (1014) are relative up and down with threaded connection hole A (1023), go up turbine (101), middle turbine (102), The lower turbine (103) penetrates into the stepped bolt through hole (1014) through the inner hexagonal bolt (1017) and is sequentially screwed into the threaded connecting hole A (1023) and is respectively connected with the threaded connecting hole B (1034), the outer wall of the lower turbine (103) is also connected with twelve groups of outer connecting cylinders (1033), the outer ends of the inner parts of the outer connecting cylinders (1033) are provided with stepped jacks, the inner sides of the inner parts of the outer connecting cylinders (1033) are provided with connecting threads, and the supporting and reinforcing structures (3) are respectively connected onto the outer connecting cylinders (1033) and supported onto the blades A (1011) and B (1021);

an upper through hole (1012) is further formed in the middle of the inner side of the upper turbine (101), an airflow baffle plate A (1013) is arranged at the top end of the upper through hole (1012), an airflow hole is formed in the middle of the airflow baffle plate A (1013), and the outer end of the airflow hole is of an arc-shaped structure;

the top end of the middle penetrating column (104) is also inserted into the upper through hole (1012), the middle of the top of the middle penetrating column (104) is provided with an air passage (1041), and the air passage (1041) is arranged from the top end of the middle penetrating column (104) to the position of the internal thread cylinder (1042) and communicated with the internal thread cylinder (1042);

the internal thread cylinder (1042) is provided with twelve groups, every two adjacent three groups are connected together, the flow-disturbing pipe (1043) penetrates through the outer end of the lower turbine (103) and is screwed into the internal thread cylinder (1042) through threads, and the outer port of the flow-disturbing pipe (1043) is of an arc-shaped structure and faces to the rotation direction of the turbine assembly (1);

an airflow baffle B (2) is movably mounted on the top end side of the air passage (1041), the airflow baffle B (2) is attached to an airflow hole in the inner side of the airflow baffle A (1013), and the outer diameter of the airflow baffle B (2) is larger than the inner diameter of the airflow hole and smaller than the inner diameter of the upper through hole (1012);

the bottom of airflow baffle B (2) is fixedly connected with guide post (201) still, and the cover is equipped with reset spring (203) and fixedly connected with guide block (202) on guide post (201), and guide block (202) activity interlude is in air flue (1041), and the outer end of guide block (202) is equipped with three fan-shaped gaps of group.

2. A turbine blade with turbulator structure based on aircraft engine as claimed in claim 1, wherein: the supporting and reinforcing structure (3) comprises a T-shaped pipe (301), a supporting plate (302) and a buffering column (303), the two ends of the T-shaped pipe (301) are respectively connected with the supporting plate (302) through the buffering column (303), the supporting plate (302) is respectively supported on a blade A (1011) and a blade B (1021), the buffering column (303) is slidably clamped in pipe sleeves at the two ends of the T-shaped pipe (301), and a buffering spring is further installed in the pipe sleeves at the two ends of the T-shaped pipe (301).

3. A turbine blade with turbulator structure based on an aircraft engine as claimed in claim 2, wherein: the other end of the T-shaped pipe (301) is inserted into a step jack at the outer end inside the outer connecting cylinder (1033), and a connecting bolt (304) penetrates through the T-shaped pipe (301) and is screwed into a connecting thread at the inner side inside the outer connecting cylinder (1033).